Abstract: A vehicle location system and method whereby the position coordinates of a vehicle are made available to other vehicles or to fixed locations by transmission of a data message containing position coordinates of the vehicle. The time slot in which the data message is transmitted is uniquely assigned to each transmitting vehicle as a function of its position in a grid segment with respect to a reference waypoint assigned to that grid segment. Position information in latitude and longitude is provided to each receiving vehicle, together with a precise timing signal, by the Global Positioning System (GPS), or by the Global Orbiting Navigational Satellite System (GLONASS), or by both systems. A synthetic latitude function and a synthetic longitude function provide a periodic mapping of a specific time period onto areas represented by grid segments charted on the global surface. These synthetic functions are initiated and controlled by the precise timing signal from the GPS or GLONASS systems.

Abstract: An omnidirectional approach slope indicator unit for heliports is disclosed. The unit may include two oppositely directed light beam generators secured to a rotatable shaft, the light beam generators generating light beams of differing colors to alert an approaching aircraft of his position relative to the glide slope indicated by the light beams.

Abstract: A location system and method whereby the azimuth and range information of an aircraft with respect to a reference ground station is made available to other aircraft by transmission of a pulse at a time uniquely associated with the aircraft's location. A synthetic azimuth function and a synthetic range function provide a periodic mapping of an area. The synthetic azimuth function is a slowed, time-expanded representation of a conventional azimuth function. Each azimuth increment is allocated a time slot in the synthetic azimuth function. The synthetic azimuth function is synchronized by counting a number of synchronizing pulses from the conventional azimuth function, and a synthetic azimuth reference pulse is periodically transmitted from a reference ground station to synchronize all aircraft using the synthetic azimuth function.

Abstract: A visual approach system for indicating the glide slope and course of an aircraft to a runway. The system includes a plurality of light beam generators of various colors enclosed by tubular light shields for precisely controlling the divergence angles of the beams. The angles of the shields with respect to each other and the runway are precisely controlled to generate an accurately positioned glide slope and course to the runway. In one embodiment a center light beam of a first color has an axis extending along the glide slope and course to the runway. In one embodiment a center light beam of a first color has an axis extending along the glide slope and course to the runway. A first pair of different colored beams extend along the top and bottom of the center beam for indicating deviations from the glide slope, and a second pair of different colored beams extend along opposite sides of the center beam for indicating deviations from the course to the runway.

Abstract: Wind conditions along the projected flight path of an aircraft are measured and displayed. Wind velocity and direction at the aircraft and at the projected touchdown or takeoff point of the aircraft are compared and the existence of a wind gradient or wind shear line along the flight path is predicted. The possible presence of a wind shear line and the velocity differential there across is used, in cooperation with altitude and airspeed information and the performance characteristics of the aircraft, to determine whether the planned maneuver may be successfully completed under the instantaneously existing wind conditions.